CA2648765C - Configurations de sortie de buse de reacteur comprenant des projections orientees relativement aux pylones et methodes et systemes connexes - Google Patents

Configurations de sortie de buse de reacteur comprenant des projections orientees relativement aux pylones et methodes et systemes connexes Download PDF

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Publication number
CA2648765C
CA2648765C CA2648765A CA2648765A CA2648765C CA 2648765 C CA2648765 C CA 2648765C CA 2648765 A CA2648765 A CA 2648765A CA 2648765 A CA2648765 A CA 2648765A CA 2648765 C CA2648765 C CA 2648765C
Authority
CA
Canada
Prior art keywords
projections
pylon
flow
projection
nozzle
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Active
Application number
CA2648765A
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English (en)
Other versions
CA2648765A1 (fr
Inventor
Vinod G. Mengle
Russell H. Thomas
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Boeing Co
Original Assignee
Boeing Co
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Boeing Co filed Critical Boeing Co
Publication of CA2648765A1 publication Critical patent/CA2648765A1/fr
Application granted granted Critical
Publication of CA2648765C publication Critical patent/CA2648765C/fr
Active legal-status Critical Current
Anticipated expiration legal-status Critical

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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02K—JET-PROPULSION PLANTS
    • F02K1/00—Plants characterised by the form or arrangement of the jet pipe or nozzle; Jet pipes or nozzles peculiar thereto
    • F02K1/38—Introducing air inside the jet
    • F02K1/386—Introducing air inside the jet mixing devices in the jet pipe, e.g. for mixing primary and secondary flow
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
    • B64D33/00—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for
    • B64D33/04—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for of exhaust outlets or jet pipes
    • B64D33/06—Silencing exhaust or propulsion jets
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02K—JET-PROPULSION PLANTS
    • F02K1/00—Plants characterised by the form or arrangement of the jet pipe or nozzle; Jet pipes or nozzles peculiar thereto
    • F02K1/46—Nozzles having means for adding air to the jet or for augmenting the mixing region between the jet and the ambient air, e.g. for silencing
    • F02K1/48—Corrugated nozzles

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Jet Pumps And Other Pumps (AREA)
  • Exhaust Silencers (AREA)

Abstract

Cette invention concerne des configurations de sortie de tuyère ainsi que des systèmes et procédés relatifs. Un système aéronautique selon un mode de réalisation comprend une tuyère d'échappement de moteur à réaction, présentant une surface d'écoulement interne et une ouverture de sortie. L'ouverture de sortie a un périmètre qui comprend des saillies multiples s'étendant dans un sens arrière. Les parties arrière des saillies individuelles avoisinantes sont mutuellement séparées par un espace. Une caractéristique géométrique des saillies multiples peut changer de manière monotone le long d'une partie au moins du périmètre. Les saillies proches d'un pylône de support et/ou d'une chemise thermique associée peuvent adopter des configurations particulières comprenant une profondeur d'immersion supérieure à celle des autres saillies.
CA2648765A 2008-08-11 2008-08-11 Configurations de sortie de buse de reacteur comprenant des projections orientees relativement aux pylones et methodes et systemes connexes Active CA2648765C (fr)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
PCT/US2008/072795 WO2010019131A1 (fr) 2008-08-11 2008-08-11 Configurations de sortie de tuyère de moteur à réaction, comprenant des saillies orientées par rapport à des pylônes, et systèmes et procédés relatifs

Publications (2)

Publication Number Publication Date
CA2648765A1 CA2648765A1 (fr) 2010-02-11
CA2648765C true CA2648765C (fr) 2011-04-19

Family

ID=40380389

Family Applications (1)

Application Number Title Priority Date Filing Date
CA2648765A Active CA2648765C (fr) 2008-08-11 2008-08-11 Configurations de sortie de buse de reacteur comprenant des projections orientees relativement aux pylones et methodes et systemes connexes

Country Status (2)

Country Link
CA (1) CA2648765C (fr)
WO (1) WO2010019131A1 (fr)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US8746613B2 (en) 2008-08-20 2014-06-10 Williams International Co., L.L.C. Jet engine exhaust nozzle and associated system and method of use

Families Citing this family (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE102010045697A1 (de) * 2010-09-16 2012-03-22 Rolls-Royce Deutschland Ltd & Co Kg Blütenmischer für ein Turbofantriebwerk
GB2492311B (en) 2011-05-20 2015-01-28 Dhayan Tomas Ishigaki Periorbital edema reduction
US9511873B2 (en) 2012-03-09 2016-12-06 The Boeing Company Noise-reducing engine nozzle system
DE102012220360A1 (de) * 2012-11-08 2014-05-08 Rolls-Royce Deutschland Ltd & Co Kg Düse mit Leitvorrichtungen
FR3012417B1 (fr) * 2013-10-31 2016-12-09 Snecma Nacelle de turboreacteur

Family Cites Families (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB1127659A (en) * 1966-09-16 1968-09-18 Rolls Royce Improvements in gas turbine engines
GB2146702B (en) * 1983-09-14 1987-12-23 Rolls Royce Exhaust mixer for turbofan aeroengine
US6360528B1 (en) * 1997-10-31 2002-03-26 General Electric Company Chevron exhaust nozzle for a gas turbine engine
US6314721B1 (en) * 1998-09-04 2001-11-13 United Technologies Corporation Tabbed nozzle for jet noise suppression
EP1076765B1 (fr) * 1999-03-05 2006-06-14 Rolls-Royce Deutschland Ltd & Co KG Melangeur en forme de fleur destine a un turboreacteur a double flux
US6983912B2 (en) * 2002-04-30 2006-01-10 The Boeing Company Hybrid exhaust heat shield for pylon mounted gas turbine engines
FR2855558B1 (fr) * 2003-05-28 2005-07-15 Snecma Moteurs Tuyere de turbomachine a reduction de bruit
GB0505246D0 (en) * 2005-03-15 2005-04-20 Rolls Royce Plc Engine noise
US7520124B2 (en) * 2006-09-12 2009-04-21 United Technologies Corporation Asymmetric serrated nozzle for exhaust noise reduction

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US8746613B2 (en) 2008-08-20 2014-06-10 Williams International Co., L.L.C. Jet engine exhaust nozzle and associated system and method of use

Also Published As

Publication number Publication date
CA2648765A1 (fr) 2010-02-11
WO2010019131A1 (fr) 2010-02-18

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